N2O4/UDMH propellant rocket stage. Loaded/empty mass 45,600/5,600 kg. Thrust 735.00 kN. Vacuum specific impulse 281 seconds.
AKA: Geostationary Satellite Launch Vehicle.
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Gross mass: 45,600 kg (100,500 lb).
Unfuelled mass: 5,600 kg (12,300 lb).
Height: 19.70 m (64.60 ft).
Diameter: 2.10 m (6.80 ft).
Span: 2.10 m (6.80 ft).
Thrust: 735.00 kN (165,234 lbf).
Specific impulse: 281 s.
Specific impulse sea level: 240 s.
Burn time: 159 s.
Number: 16 .
Viking 2 SEP N2O4/UDMH rocket engine. 693 kN. In production. Isp=281s. Used on Ariane 1, GSLV space launchers. First flight 1979. More...
Associated Launch Vehicles
GSLV Indian mixed-propulsion orbital launch vehicle for geosynchronous satellites using a Lox/LH2 upper stage developed from Russian technology. More...
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
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